U.S. patent number 8,876,057 [Application Number 12/373,537] was granted by the patent office on 2014-11-04 for aerodynamic integration of a payload container with a vertical take-off and landing aircraft.
This patent grant is currently assigned to Sikorsky Aircraft Corporation. The grantee listed for this patent is Mark R. Alber, Alfred Russell Smiley, Brandon L. Stille. Invention is credited to Mark R. Alber, Alfred Russell Smiley, Brandon L. Stille.
United States Patent |
8,876,057 |
Alber , et al. |
November 4, 2014 |
Aerodynamic integration of a payload container with a vertical
take-off and landing aircraft
Abstract
A vertical takeoff and landing (VTOL) rotary-wing air-craft is
sized and configured to match a payload container such as a
standardized Joint Modular Intermodal Container (JMIC). The
aircraft may be an Unmanned Air Vehicle (UAV) that is capable of
autonomously engaging and disengaging the container so that the
aircraft can pick up and drop off the JMIC with minimum human
intervention.
Inventors: |
Alber; Mark R. (Milford,
CT), Stille; Brandon L. (Cheshire, CT), Smiley; Alfred
Russell (Marlborough, CT) |
Applicant: |
Name |
City |
State |
Country |
Type |
Alber; Mark R.
Stille; Brandon L.
Smiley; Alfred Russell |
Milford
Cheshire
Marlborough |
CT
CT
CT |
US
US
US |
|
|
Assignee: |
Sikorsky Aircraft Corporation
(Stratford, CT)
|
Family
ID: |
39609212 |
Appl.
No.: |
12/373,537 |
Filed: |
July 19, 2007 |
PCT
Filed: |
July 19, 2007 |
PCT No.: |
PCT/US2007/073846 |
371(c)(1),(2),(4) Date: |
January 13, 2009 |
PCT
Pub. No.: |
WO2008/085547 |
PCT
Pub. Date: |
July 17, 2008 |
Prior Publication Data
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Document
Identifier |
Publication Date |
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US 20100012769 A1 |
Jan 21, 2010 |
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Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
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60834104 |
Jul 27, 2006 |
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Current U.S.
Class: |
244/137.1;
244/172.3 |
Current CPC
Class: |
B64C
39/024 (20130101); B64C 27/10 (20130101); B64C
39/02 (20130101); B64C 2201/128 (20130101); B64C
2201/024 (20130101); B64C 2027/8236 (20130101) |
Current International
Class: |
B64C
1/22 (20060101) |
Field of
Search: |
;244/6,7R,137.1,137.4,17.11,17.23 |
References Cited
[Referenced By]
U.S. Patent Documents
Other References
PCT International Search Report and written opinion mailed Aug. 27,
2008. cited by applicant .
Supplementary European Search Report for European Patent
Application No. 07872257.6 dated Mar. 7, 2013. cited by
applicant.
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Primary Examiner: O'Hara; Brian M
Attorney, Agent or Firm: Carlson, Gaskey & Olds,
P.C.
Parent Case Text
The present application claims priority to U.S. Provisional Patent
Application Ser. No. 60/834,104, filed Jul. 27, 2006.
Claims
What is claimed is:
1. A vertical takeoff and landing (VTOL) aircraft comprising: an
airframe which defines a cargo tunnel along a longitudinal axis of
said airframe, said cargo tunnel interfaces with a first surface of
a payload container and extends at least partially along a second
side and a third side of the payload container, wherein said cargo
tunnel has an axial length that is longer than a length of the
payload container, a landing gear system that retracts to
selectively vertically position the cargo tunnel relative to the
payload container when said landing gear system is in contact with
ground.
2. The aircraft as recited in claim 1, wherein said aircraft is
unmanned.
3. The aircraft as recited in claim 1, wherein the first surface is
an upper surface of the payload container.
4. The aircraft as recited in claim 1, wherein said cargo tunnel
includes an open forward cargo tunnel section which opens through a
forward section of said airframe such that the payload container
may transit along a longitudinal axis of the airframe through said
open forward cargo tunnel section.
5. The aircraft as recited in claim 1, wherein said cargo tunnel
includes an at least partially closed aft section.
6. The aircraft as recited in claim 5, wherein said aft section
includes a propulsive system.
7. The aircraft as recited in claim 1, wherein said cargo tunnel
includes a first tunnel surface, a second tunnel surface transverse
to said first tunnel surface and a third tunnel surface transverse
to said first tunnel surface.
8. The aircraft as recited in claim 7, wherein said cargo tunnel
includes an open forward cargo tunnel section which opens through a
forward section of said airframe such that the payload container
may transit along a longitudinal axis of the airframe through said
open forward cargo tunnel section.
9. The aircraft as recited in claim 7, wherein said second tunnel
surface and said third tunnel surface are defined by respective
port and starboard sponsons of said airframe.
10. The aircraft as recited in claim 9, wherein said port and
starboard sponsons of said airframe are each operable to support an
external fuel tank.
11. The aircraft as recited in claim 1, wherein said airframe
includes a propulsive system.
12. The aircraft as recited in claim 11, wherein said cargo tunnel
has an open bottom and the payload container received within said
cargo tunnel has a downwardly facing surface detached from any
portion of said aircraft.
13. The aircraft as recited in claim 1, wherein said airframe
includes a dual, counter-rotating, coaxial rotor system having an
axis of rotation that intersects the payload container, each rotor
system of said dual, counter-rotating, coaxial rotor system having
a plurality of blades.
14. The aircraft as recited in claim 1, wherein said cargo tunnel
has an open bottom, such that the payload container received within
said cargo tunnel has a downwardly facing surface that is
completely exposed.
15. The aircraft as recited in claim 1, including an aerodynamic
structure to define an aerodynamic interface forward of the payload
container, said aerodynamic structure moveable about a generally
horizontal axis.
16. The aircraft as recited in claim 1, wherein said landing gear
system is configured to retract forward.
17. A vertical takeoff and landing (VTOL) aircraft comprising: an
airframe which defines a cargo tunnel along a longitudinal axis of
said airframe, said cargo tunnel interfaces with a first surface of
a payload container and extends at least partially along a second
side and a third side of the payload container; and a dual,
counter-rotating, coaxial rotor system which defines an axis of
rotation, said axis of rotation intersects said first surface of
the payload container when the payload container is held within
said cargo tunnel a landing gear system selectively positionable
relative to said airframe when contacting ground to vertically
position said cargo tunnel relative to the payload container to
attach said upper surface to said payload container when said
aircraft is on the ground.
18. The aircraft as recited in claim 17, wherein said aircraft is
unmanned.
19. The aircraft as recited in claim 17, wherein the first surface
is an upper surface of the payload container, and said cargo tunnel
has an axial length that is longer than a length of the payload
container.
20. The aircraft as recited in claim 17, wherein said cargo tunnel
includes an open forward cargo tunnel section which opens through a
forward section of said airframe such that the payload container
may transit along a longitudinal axis of the airframe through said
open forward cargo tunnel section.
21. The aircraft as recited in claim 17, wherein said cargo tunnel
includes an at least partially closed aft section, said aft section
includes a propulsive system operable to provide translational
thrust.
22. The aircraft as recited in claim 17, wherein said cargo tunnel
includes a first tunnel surface, a second tunnel surface transverse
to said first tunnel surface and a third tunnel surface transverse
to said first tunnel surface, said cargo tunnel includes an open
forward cargo tunnel section which opens through a forward section
of said airframe such that the payload container may transit along
a longitudinal axis of the airframe through said open forward cargo
tunnel section.
23. The aircraft as recited in claim 17, wherein said cargo tunnel
includes a first tunnel surface, a second tunnel surface transverse
to said first tunnel surface and a third tunnel surface transverse
to said first tunnel surface, said second tunnel surface and said
third tunnel surface are defined by respective port and starboard
sponsons of said airframe said first tunnel surface defined by a
vertically upper surface of said cargo tunnel.
24. The aircraft as recited in claim 23, wherein said port and
starboard sponsons of said airframe are each operable to support an
external fuel tank.
25. The aircraft as recited in claim 17, wherein said cargo tunnel
provides at least partial conformal carriage of the payload
container.
26. The aircraft as recited in claim 17, further comprising an
aerodynamic structure to define an aerodynamic interface forward of
the payload container, said aerodynamic structure moveable about a
generally horizontal axis.
27. The aircraft as recited in claim 17, wherein each rotor of said
dual, counter-rotating, coaxial rotor system includes more than two
blades.
28. The aircraft as recited in claim 17, wherein said landing gear
system is configured to retract forward to selectively position
said landing gear system relative to said airframe.
29. A vertical takeoff and landing (VTOL) aircraft comprising: an
airframe which defines a cargo tunnel along a longitudinal axis of
said airframe, said cargo tunnel interfaces with a first surface of
a payload container and extends at least partially along a second
side and a third side of the payload container; and an aerodynamic
structure forward of the payload container to define an aerodynamic
interface forward of the payload container, wherein said cargo
tunnel has an axial length that is longer than a length of the
payload container a landing gear system that is retractable when
said aircraft is on ground to selectively position the cargo tunnel
vertically when said aircraft is on ground.
30. The aircraft as recited in claim 29, further comprising a dual,
counter-rotating, coaxial rotor system which defines an axis of
rotation, said axis of rotation intersects the payload container,
each rotor system of said dual, counter-rotating, coaxial rotor
system having a plurality of blades.
31. The aircraft as recited in claim 29, wherein said aircraft is
unmanned.
32. The aircraft as recited in claim 29, wherein said cargo tunnel
provides at least partial conformal carriage of the payload
container.
33. The aircraft as recited in claim 29, wherein said cargo tunnel
has an open bottom and the payload container received within said
cargo tunnel has a downwardly facing surface detached from any
portion of said aircraft.
34. The aircraft as recited in claim 29, wherein said landing gear
system is configured to retract forward to position the cargo
tunnel.
Description
BACKGROUND OF THE INVENTION
The present invention relates to an aircraft sized and configured
to transport a payload container, and more specifically to a
Vertical Take-off and Landing (VTOL) unmanned air vehicle (UAV)
that is aerodynamically and structurally designed around a
standardized container such as a Joint Modular Intermodal Container
(JMIC) to facilitate autonomous pickup, transport, and drop-off of
the container.
Future military forces require enhanced vertical lift capabilities
in a compact package to transport payloads into hostile
environments.
Internal load operations provide secure aerodynamic carriage of
payloads. However, as advantageous as internal load operations may
be, such operations may be relatively time consuming and
complicated to execute. One such complication may be the relatively
small clearances associated with onloading and offloading cargo
over a cargo ramp and into the aircraft internal cargo bay.
Internal load operations typically require personnel to operate as
spotters who communicate with vehicle drivers or ground based
equipment operators such as forklift drivers to facilitate position
of cargo within the aircraft cargo bay.
External load operations provide a rapid procedure to load,
transport, and unload cargo. One or more lines having cargo hooks
at an end thereof, or a set of slings, are used to attach the cargo
to the aircraft for transportation. However, as advantageous as
external operations may be, external operations may also be
relatively complicated and time consuming to execute. One such
complication is cargo hook positioning. The process of attaching
and detaching the cargo hooks to a load generally requires an
aircrew member to visually observe the payload and direct a pilot
via an intercom system. Although effective, this process may be
relatively time consuming and may be hampered by the time lag
between communication of aircraft current position and pilot
reaction.
Accordingly, it is desirable to provide a Vertical Take-off and
Landing (VTOL) aircraft that is aerodynamically and structurally
designed around a standardized container to facilitate transport
thereof.
SUMMARY OF THE INVENTION
The vertical takeoff and landing (VTOL) rotary-wing aircraft
according to the present invention is sized and configured to match
a payload container such as a standardized Joint Modular Intermodal
Container (JMIC). The aircraft may be an Unmanned Air Vehicle (UAV)
that is capable of autonomously engaging and disengaging the
payload container with minimal or no human intervention.
The airframe defines a cargo tunnel along the longitudinal axis.
The cargo tunnel provides an open forward cargo tunnel section
which opens through a forward section of the airframe. The cargo
tunnel provides an external conformal interface which is sized to
receive the payload container. The tunnel surface is defined in
part by a respective port sponson and starboard sponson which are
aerodynamically contoured to receive an external fuel tank.
The port sponson and starboard sponson contain a retractable main
landing gear system while a tail section includes fixed tail gear.
The retractable main landing gear system retracts forward to
selectively position the airframe and the cargo tunnel relative to
the payload container for attachment thereto. Forward retraction of
the retractable main landing gear system also allows the aircraft
to squat for transport within a compact cubic space.
The aircraft also incorporates a moveable aerodynamic structure
which provides an aerodynamic interface between the cargo tunnel
and the payload container.
The present invention therefore provides a Vertical Take-off and
Landing (VTOL) aircraft that is aerodynamically and structurally
designed around a standardized container to facilitate transport
thereof.
BRIEF DESCRIPTION OF THE DRAWINGS
The various features and advantages of this invention will become
apparent to those skilled in the art from the following detailed
description of the currently disclosed embodiment. The drawings
that accompany the detailed description can be briefly described as
follows:
FIG. 1A is a side perspective view of a VTOL UAV with a payload
container attached;
FIG. 1B is a top perspective view of a VTOL UAV with a payload
container attached;
FIG. 1C is a front perspective view of a VTOL UAV with a payload
container attached;
FIG. 2 is a front perspective view of a VTOL UAV illustrating a
cargo tunnel without a payload container;
FIG. 3A is a perspective view of a payload container;
FIG. 3B is a perspective view of a VTOL UAV illustrating the
loading of a payload container along a longitudinal axis;
FIG. 3C is a bottom rear aspect perspective view of a VTOL UAV with
a payload container in an attached position;
FIG. 3D is an upper front aspect perspective view of a VTOL UAV
with a payload container in an attached position;
FIG. 4 is a perspective view of a VTOL UAV in a squat position with
the rotor blades removed as would be typical of a transport
condition;
FIG. 5A is a frontal aspect lower perspective view illustrating an
aerodynamic structure in a retracted position;
FIG. 5B is a frontal aspect lower perspective view illustrating the
aerodynamic structure of FIG. 5A in a deployed position;
FIG. 6A is a frontal aspect lower perspective view illustrating
another aerodynamic structure in a retracted position;
FIG. 6B is a frontal aspect lower perspective view illustrating the
aerodynamic structure of FIG. 6A in a deployed position;
FIG. 7A is a frontal aspect lower perspective view illustrating
another aerodynamic structure in a retracted position;
FIG. 7B is a frontal aspect lower perspective view illustrating the
aerodynamic structure of FIG. 7A in a deployed position;
FIG. 8A is a frontal aspect lower perspective view illustrating
another aerodynamic structure in a retracted position;
FIG. 8B is a frontal aspect lower perspective view illustrating the
aerodynamic structure of FIG. 8A in a deployed position; and
FIG. 9 is a front view of a VTOL UAV illustrating a multiple of
payload containers tailored to specific missions.
DETAILED DESCRIPTION OF THE DISCLOSED EMBODIMENT
FIG. 1A-1C illustrates an exemplary unmanned vertical takeoff and
landing (VTOL) rotary-wing aircraft 10 having a dual,
counter-rotating, coaxial rotor system 12 which rotates about an
axis of rotation A. The aircraft 10 includes an airframe 14 which
supports the dual, counter rotating, coaxial rotor system 12 as
well as a propulsive system T which provides translational thrust
generally parallel to an aircraft longitudinal axis L. Although a
particular high-speed VTOL Unmanned Aerial Vehicle (UAV)
configuration is illustrated and described in the disclosed
embodiment, other manned and unmanned configurations and/or
machines, such as high speed compound rotary wing aircraft with
supplemental translational thrust systems, dual contra-rotating,
coaxial rotor system aircraft, turbo-props, tilt-rotors and
tilt-wing aircraft, will also benefit from the present
invention.
The dual, counter-rotating, coaxial rotor system 12 includes an
upper rotor system 16 and a lower rotor system 18. Each rotor
system 16, 18 includes a plurality of rotor blade assemblies 20
mounted to each of an upper rotor hub assembly 22 and a lower rotor
hub assembly 24 for rotation about the rotor axis of rotation A. It
should be understood that any number of rotor blade assemblies 20
may be mounted to each rotor hub assembly 22, 24. The rotor system
12 preferably includes a rotor hub fairing system 26 for the upper
and lower rotor systems 16, 18 such that the rotor hub assemblies
22, 24 are at least partially contained therein.
The propulsive system T may include a pusher propeller 28 having a
propeller rotational axis R oriented substantially horizontal and
along the aircraft longitudinal axis L to provide thrust for
high-speed flight.
The airframe 14 defines a cargo tunnel 30 (best seen in FIGS. 1C
and 2) along the longitudinal axis L. The cargo tunnel 30 includes
a first tunnel surface 32, a second tunnel surface 34 transverse to
the first tunnel surface 32 and a third tunnel surface 36
transverse to the first tunnel surface 32 (FIG. 2). The cargo
tunnel 30 provides an open forward cargo tunnel section 38 which
opens through a forward section 14A of the airframe 14. Although
the disclosed embodiment of the cargo tunnel 30 is generally
rectilinear in lateral cross-section other shapes designed around a
particular container may also be provided.
The cargo tunnel 30 provides an external conformal interface sized
to receive a payload container P (FIG. 3A). The payload container
may be a standardized Joint Modular Intermodal Container (JMIC).
The JMIC is a stackable, interlocking reusable pallet/crate hybrid
designed for use in asset-based packaging logistics operations. The
JMIC is 52.times.44.times.42 inches in size. The cargo tunnel 30 is
sized to receive one JMIC to provide an external conformal
interface in the disclosed embodiment, however, aircraft of other
sizes may alternatively be sized to receive a multiple of payload
containers or a payload container of a different size.
The open forward cargo tunnel section 38 opens through a forward
section 14A of the airframe 14 such that the payload container P
may transit along the longitudinal axis L of the airframe 12 for
loading therein (FIGS. 3B-3D). The first tunnel surface 32 defines
the upper surface of the cargo tunnel 30 and includes a payload
container interface 40 to receive the payload container P. It
should be understood that various payload container interfaces 40
such as hooks, locks and other interfaces may be provided to
receive the payload container.
Referring to FIG. 2, the airframe 14 second tunnel surface 34 and
third tunnel surface 36 are defined in part by a respective
starboard sponson 42 and port sponson 44. The starboard sponson 42
and port sponson 44 are aerodynamically contoured to provide
conformal support (FIG. 2) for an external fuel tank 50
(illustrated attached in FIGS. 1A-1C and 3B-3D). In the disclosed
embodiment, the two external fuel tanks 50 provide greater capacity
than the internal fuel capacity to further facilitate the modular
mission driven nature of the aircraft.
The starboard sponson 42 and port sponson 44 contain a retractable
main landing gear system 52. A tail section 54 includes horizontal
stabilizers 46, 48, and vertical stabilizers 56. The vertical
stabilizers 56 each include fixed tail gear 58 (best seen in FIG.
1B). The retractable main landing gear system 52 retracts forward
to selectively position the airframe 14 and to vertically position
the cargo tunnel 30 relative to the payload container P for
attachment thereto. That is, the retractable main landing gear
system 52 is movable even when the aircraft is on the ground so as
to position the cargo tunnel 30 relative to the payload container
P.
Forward retraction of the retractable main landing gear system 52
also allows the aircraft to squat for transport within a compact
cubic space C (FIG. 4). Removal of the rotor blades and location of
the external fuel tanks 50 within the cargo tunnel 30 further
facilitates the transportable nature of the aircraft. It should be
understood that various foldable or removable structures may
alternatively or additionally be provided to further provide
compact transport.
Referring to FIG. 5A, the aircraft 10 also incorporates a movable
aerodynamic structure 60 which provides an aerodynamic interface
between the cargo tunnel 30 and the payload container P. The
aerodynamic structure 60 deploys to provide drag reduction through
payload form factor tailoring. The aerodynamic structure 60 may
include a secondary aerodynamic structure 62 which articulates
between a load position (FIG. 5A) and a flight position (FIG. 5B).
It should be understood that the aerodynamic structure 60 may move
through various articulated positions to accommodate various
payloads. The aerodynamic structure is located forward and aft of
the payload container P.
Referring to FIG. 6A, the aerodynamic structure 60A may
alternatively include an aerodynamic tarp 66 which selectively
deploys at least partially around the payload container P (FIG.
5B). That is, the aerodynamic tarp 66 unrolls over the payload
container P to provide an aerodynamic surface to surround the
rectilinear payload container P.
Referring to FIG. 7A, the aerodynamic structure 60B may
alternatively include a smart structure 68 which changes shape
(FIG. 7B) to provide an aerodynamic interface to the rectilinear
payload container P.
Referring to FIG. 8A, the aerodynamic structure 60C may
alternatively include a pneumatic inflatable structure 70A, 70B
which are selectively inflated (FIG. 8B) to provide an aerodynamic
surface about the rectilinear payload container P. It should be
understood that other deployable aerodynamic structure may
alternatively or additionally be provided.
There is an increased emphasis on the use of unmanned air vehicles
(UAV) for performing various activities in both civilian and
military situations where the use of manned flight vehicles may not
be appropriate. In addition to autonomous cargo delivery, UAV
missions may include surveillance, reconnaissance, target
acquisition, target designation, data acquisition, communications
relay, decoy, jamming, harassment, ordinance delivery, and many
others. The aircraft 14 may therefore receive mission specific
payload Containers P1-P6 (FIG. 9) to perform any such mission.
In operation, the aircraft 10 of the disclosed embodiment is a VTOL
UAV that autonomously engages and disengages the payload container
P which thereby permits, for example, the transport of payload
containers into hostile environments with minimum human
intervention. In one scenario, such as pre-positioning of material,
the aircraft 10 transports and drops-off the payload container to a
desired destination such that when personnel later arrive, the
payload container(s) will already be waiting. In another scenario,
such as re-supply during a firefight, the payload container is
released from the aircraft autonomously at a desired site such that
focus will remain on the fight and removal of the payload container
contents can occur when time or circumstances permit. In still
another scenario such as a medical evacuation, the position of a
payload container is transmitted to an aircraft 10 which
autonomously lands adjacent he payload container, taxies over the
payload container; adjust the aircraft main landing gear height to
receive the payload container within the cargo tunnel; then
egresses from the area of operations.
It should be understood that relative positional terms such as
"forward," "aft," "upper," "lower," "above," "below," and the like
are with reference to the normal operational attitude of the
vehicle and should not be considered otherwise limiting.
It should be understood that although a particular component
arrangement is disclosed in the illustrated embodiment, other
arrangements will benefit from the instant invention.
Although particular step sequences are shown, described, and
claimed, it should be understood that steps may be performed in any
order, separated or combined unless otherwise indicated and will
still benefit from the present invention.
The foregoing description is exemplary rather than defined by the
limitations within. Many modifications and variations of the
present invention are possible in light of the above teachings. The
disclosed embodiments of this invention have been disclosed,
however, one of ordinary skill in the art would recognize that
certain modifications would come within the scope of this
invention. It is, therefore, to be understood that within the scope
of the appended claims, the invention may be practiced otherwise
than as specifically described. For that reason the following
claims should be studied to determine the true scope and content of
this invention.
* * * * *